A fast approach for unsteady compressor performance simulation under boundary condition caused by pressure gain combustion

Neumann, Nicolai; Asli, Majid; Garan, Niclas; Peitsch, Dieter; Stathopoulos, Panagiotis

doi:10.1016/j.applthermaleng.2021.117223

Cited by 11 publications

(3 citation statements)

References 21 publications

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“…Although the historical reasons for applying low-AR designs are valid, new design features such as intentional mistuning [13] and blade design methods to reduce clearance sensitivity [14] could potentially re-open the field for high-AR compressor design. The efficiency of gas turbines engines, depending on the turbomachine's performance (compressors and turbines), can be improved by innovations including engines with rotating detonation [15] and pulse detonation combustion [16].…”

Section: Introductionmentioning

confidence: 99%

Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance

Silva,

Grönstedt,

Xisto

et al. 2024

Aerospace

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The ratio between blade height and chord, named the aspect ratio (AR), plays an important role in compressor aerodynamic design. Once selected, it influences stage performance, blade losses and the stage stability margin. The choice of the design AR involves both aerodynamic and mechanical considerations, and an aim is frequently to achieve the desired operating range while maximizing efficiency. For a fixed set of aerodynamic and geometric parameters, there will be an optimal choice of AR that achieves a maximum efficiency. However, for a state-of-the-art aero-engine design, optimality means multi-objective optimality, that is, reaching the highest possible efficiency for a number of operating points while achieving a sufficient stability margin. To this end, the influence of the AR on the performance of the first rotor row of a multistage, multi-objective, high-speed compressor design is analyzed. A careful setup of the high-speed aerodynamic design problem allows the effect of the AR to be isolated. Close to the optimal AR, only a modest efficiency variation is observed, but a considerable change in compressor stability margin (SM) is noted. Decreasing the AR allows for increasing efficiency, but at the expense of a reduced surge margin. This allows the designer to trade efficiency for stability. Increasing the AR, however, is shown to reduce both the surge margin and efficiency; hence, a distinct optimality in stability is observed for the analyzed rotor blade row. In this work, optimality in the surge margin with respect to the AR is observed, whereas there is a close to optimal efficiency. The predicted range from AR = 1.10 to AR = 1.64 is only indicative, considering that the definition of multi-objective optimality requires balancing efficiency and the surge margin and that the choice of balancing these two criteria requires making a design choice along a pareto optimal front.

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Section: Introductionmentioning

confidence: 99%

Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance

Silva,

Grönstedt,

Xisto

et al. 2024

Aerospace

View full text Add to dashboard Cite

show abstract

“…Although the historical reasons to apply low AR designs are valid, new design features such as intentional mistuning [13] and blade design methods to reduce clearance sensitivity [14], could potentially re-open the field for high AR compressor design. The efficiency of gas turbines engines, depending on the turbomachine's performances (compressors [15] and turbines), including engines with rotating detonation [16] and pulse detonation combustion [17].…”

Section: Introductionmentioning

confidence: 99%

Analysis of Blade Aspect Ratio Influence on High-Speed Axial Compressor Performance

Silva,

Grönstedt,

Xisto

et al. 2024

Preprint

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The ratio between blade height and chord, named aspect ratio (AR), plays an important role in compressor aerodynamic design. Once selected, it influences stage performance, blade losses, and the stage stability margin. The choice of the design AR involves both aerodynamic and mechanical considerations, and a reasonable aim is frequently to achieve a desired operating range while maximizing efficiency. For a fixed set of aerodynamic and geometric parameters there will be an optimal choice in AR that achieves a maximum efficiency. However, for a state-of-the-art aero-engine design optimality means multi-objective optimality, that is reaching the highest possible efficiency for a number of operating points while achieving a sufficient stability margin. To this end, the influence of the AR on the performance of the first rotor row of a multistage multi-objective high-speed compressor design is analyzed. A careful setup of the high-speed aerodynamic design problem allows the effect of the AR to be isolated. Close to the optimal AR, only a modest efficiency variation is observed, but a considerable change in compressor stability margin (SM) is noted. Decreasing the AR allows for an increasing efficiency, but at the expense of a reduced surge margin. This allows the designer to trade efficiency for stability. Increasing the AR, however, is shown to reduce both surge margin and efficiency, hence a distinct optimality in stability is observed for the analyzed rotor blade row. In this work, the optimality in surge margin with respect to AR is observed whereas a close to optimal efficiency. The predicted range from AR=1.10 to AR=1.64, is only indicative, considering that the definition of a multi-objective optimality requires balancing efficiency and surge margin and that the choice of balancing these two criteria requires making a design choice along a pareto optimal front.

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“…Bayindir 15 conducted numerical investigations to study the flow field of the compressor by applying periodic pressure fluctuations (0.28-0.48 MPa, 80 Hz) at the compressor outlet. Many experimental and numerical studies had been done at TU Berlin [16][17][18][19] to describe the flow field of various compressor cascades with periodic non-steady boundary conditions. Flow control methods were utilized to stabilize the flow in the cascades.…”

Section: Introductionmentioning

confidence: 99%

Numerical studies on interactions between a centrifugal compressor and the back-propagated pressure waves originated from a pulse detonation combustor

Lü

Wang

Zhang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part A:

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In order to investigate the influence of the back-propagated pressure waves originated from a pulse detonation combustor on the operating characteristics of the compressor in the pulse detonation turbine engine, a model consist of a centrifugal compressor and an isolation section which was usually utilized to decrease the peak value of the back-propagated pressure waves was set up. Numerical simulations were carried out to study the interactions between the centrifugal compressor and the back-propagated pressure waves under different operating conditions. The matching characteristics of the compressor under the influence of the back-propagated pressure waves were analyzed in a detonation cycle. The results showed that the back-propagated pressure waves would push the shock wave in the isolator towards the throat position, but the shock wave did not pass through the throat for the compressor corrected speed of n = 100% and n = 105%. For these two cases, the back-propagated pressure waves were completely isolated and the operating characteristics of the compressor were the same as those under the steady outlet conditions. For the corrected speed of n = 50% and n = 90%, the shock wave in the isolator section was pushed out of the throat and the supersonic flow in the isolator section was destroyed under the influence of the back-propagated pressure waves. The back-propagated pressure waves would propagate upstream into the compressor. Consequently, the instantaneous mass flow rate and the torque acting on the centrifugal impeller was decreased. The work required by the compressor was also reduced. The equivalent isentropic efficiency of the compressor was decreased. The separation or backflow in the compressor caused by the back-propagated pressure waves would results in an equivalent isentropic efficiency loss of 3.2% points for the case of n = 90% and 15.6% points for the case of n = 50%.

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A fast approach for unsteady compressor performance simulation under boundary condition caused by pressure gain combustion

Cited by 11 publications

References 21 publications

Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance

Analysis of Blade Aspect Ratio’s Influence on High-Speed Axial Compressor Performance

Analysis of Blade Aspect Ratio Influence on High-Speed Axial Compressor Performance

Numerical studies on interactions between a centrifugal compressor and the back-propagated pressure waves originated from a pulse detonation combustor

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